CN114264446B - Multi-degree-of-freedom pose-adjustable electric propulsion plume test tool - Google Patents
Multi-degree-of-freedom pose-adjustable electric propulsion plume test tool Download PDFInfo
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- CN114264446B CN114264446B CN202111587813.1A CN202111587813A CN114264446B CN 114264446 B CN114264446 B CN 114264446B CN 202111587813 A CN202111587813 A CN 202111587813A CN 114264446 B CN114264446 B CN 114264446B
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The application belongs to the technical field of equipment tools, and particularly relates to an electric propulsion plume test tool with adjustable multiple degrees of freedom and positions, which comprises a tool, wherein the tool comprises a test piece bracket, a slide block guiding turntable and a tool lifting lug, one surface of the slide block guiding turntable is provided with a cross-shaped track, the other surface of the slide block guiding turntable is provided with a hinge mechanism, the slide block guiding turntable can rotate along a central shaft of the hinge mechanism, the hinge mechanism is connected with the tool lifting lug through a rotating shaft pin, the test piece bracket is of a rectangular frame structure, the number of the test piece brackets is four, the heads and the tails of the test piece brackets are mutually hinged to form a frame with a diamond cross section, four corners of the frame are provided with guide rail sliding blocks, and the guide rail sliding blocks can move along the track. The application provides an electric propulsion plume test tool with multiple degrees of freedom and adjustable pose.
Description
Technical Field
The application belongs to the technical field of equipment tools, and particularly relates to an electric propulsion plume test tool with multiple degrees of freedom and adjustable pose.
Background
The prior art comprises the following steps:
the electric propeller is a device which can generate thrust without depending on the combustion of chemical propellant, and has the characteristics of higher than impulse, long service life and small thrust. Future electric thrusters will find widespread use in satellite platforms to ensure that the satellite maintains a fixed point orbital position during orbiting while increasing the loading capacity of the satellite.
Solar arrays are important devices for powering satellite loads. The solar cell array can generate continuous electric energy through the photoelectric effect, meets the electricity demand of a satellite platform and load in an illumination area, charges a storage battery and meets the electricity demand of a shadow area. When the satellite uses the electric propeller to carry out orbit correction, the sprayed ion flow can generate irreversible sputtering corrosion on the solar cell array, and meanwhile, particles generated by plume sputtering can pollute the surface of the solar cell after being redeposited. Therefore, in the design process of the satellite solar cell array containing the working condition, a large number of ground tests and simulation analysis of the influence test of the electric propulsion plumes on the solar cell array are required to obtain the distribution and flux data of the electric propulsion plumes, and meanwhile, the influence degree of the electric propulsion plumes on the solar cell in the whole life cycle of the satellite is simulated, so that the satellite solar cell array is improved.
However, the present inventors have found that the above prior art has at least the following technical problems:
because the injection angle of the plume of the electric propeller and the posture adjustment of the solar cell array can be coupled to generate a test working condition of the posture of multiple degrees of freedom, the conventional tooling equipment is insufficient for supporting smooth development of a plume test, and meanwhile, the complexity of the environment of the spatial particles of the plume field also increases the difficulty of simulation. The multi-degree-of-freedom pose-adjustable electric propulsion plume test tool for simulating the relative positions of the satellite solar cell array and the electric propulsion device can solve the test problems.
Difficulty and meaning for solving the technical problems:
therefore, based on the problems, the electric propulsion plume test tool with the multiple degrees of freedom and the adjustable pose is provided, the injection angle of the satellite electric propulsion plume relative to the solar cell array can be accurately simulated in the ground environment, and plume test devices such as a solar cell module, circuit raw materials and components can be placed on a test piece bracket of the tool, so that the tool can be applied to ground tests for simulating the influence of the electric propulsion plume on the solar cell array, and provides a test research basis for improving the reliability of the solar cell array, and has important practical significance.
Disclosure of Invention
The application aims to provide an electric propulsion plume test tool with multiple degrees of freedom and adjustable pose for solving the technical problems in the prior art.
The technical scheme adopted by the embodiment of the application for solving the technical problems in the prior art is as follows:
the utility model provides a multi freedom position appearance adjustable electric propulsion plume test fixture, multi freedom position appearance adjustable electric propulsion plume test fixture includes the frock, the frock includes test piece bracket, slider direction revolving stage and frock lug, slider direction revolving stage one side is equipped with the track of "cross" font, and the another side is equipped with hinge mechanism, the slider direction revolving stage can rotate along hinge mechanism's center pin, hinge mechanism passes through the pivot pin with the frock lug to be connected, test piece bracket is rectangular frame structure, the quantity of test piece bracket is four and the frame that the head and the tail articulated constitution cross section is diamond each other, the four corners department of frame is equipped with the guide rail slider, the guide rail slider can follow the track and remove.
The embodiment of the application can also adopt the following technical scheme:
in the multi-degree-of-freedom pose-adjustable electric propulsion plume test tool, further, the tool is arranged in a vacuum tank body, and an electric propeller in the vacuum tank body can spray plume particles to the tool.
In the electric propulsion plume test tool with the adjustable pose and multiple degrees of freedom, further, the tool lifting lug is provided with the corner dial A, and zero graduation lines of the corner dial A are parallel to the central axis of the tool lifting lug.
In the electric propulsion plume test tool with the adjustable pose and multiple degrees of freedom, further, the rotating angle dial B is arranged on the sliding block guiding turntable.
In the electric propulsion plume test tool with the adjustable pose and multiple degrees of freedom, further, a corner dial C is arranged at one corner of the frame, and zero graduation lines of the corner dial C are parallel to one side of the frame.
One or more technical solutions provided in the embodiments of the present application have at least the following beneficial effects:
1. the application can accurately simulate the angle of the satellite electric propeller for carrying out plume injection on any posture of the solar cell array in the ground environment, can be used for regulating the posture of the electric propeller plume for the solar cell array influence test, has the characteristic of adjustable three degrees of freedom, meets the current working condition of coupling all satellite electric propulsion plume injection angles with the solar cell array posture regulation diversity, and provides technical support for ground environment simulation for the influence of the touch electric propeller plume on the solar cell array.
2. The gesture of the application has readability, each rotating link is provided with a dial for angle measurement, and any angle adjustment is all known.
3. The application has simple structure, can be integrally made of aluminum profiles and has the characteristic of light structure.
Drawings
FIG. 1 is a schematic diagram of the installation and use of an electric propulsion plume test tool with multiple degrees of freedom and adjustable pose;
FIG. 2 is an assembly view of a tooling;
FIG. 3 is a left side view of the tooling;
figure 4 (a) is a front view of a slider guide turntable,
FIG. 4 (b) is a cross-sectional view taken along the direction A-A of FIG. 4 (a) of the specification,
FIG. 4 (c) is an isometric view of a slider guide turret;
FIG. 5 is a block diagram of a test piece carrier;
fig. 6 is an assembly view of a test piece.
In the figure:
1. a tool; 2. a vacuum tank; 3. an electric propeller; 4. a guide rail slide block; 5. a test piece carrier; 6. the slide block guides the rotary table; 7. tool lifting lugs; 8. a rotation angle dial A; 9. a rotation angle dial B; 10. a rotation angle dial C; 11. a rotating shaft pin; 12. a stepped through hole; 13. a battery panel; 14. an aluminum plate bracket; 15. and a glass cover sheet.
Detailed Description
In order to better understand the above technical solutions, the following detailed description will refer to the accompanying drawings and specific embodiments.
Example 1
The embodiment comprises a tool lifting lug 7 with a corner dial A8, which is used for simulating the angle of rotation posture adjustment of the solar cell array; the two-degree-of-freedom sliding block with the corner dial B9 is guided to the rotary table 6 and is used for simulating the swing angle of the electric propeller on the star; the test piece carrier 5 assembly is used for placing test pieces including, but not limited to, single solar cells, wires, coated glass cover plates, and the like. The whole test tool comprises three corner dials, namely a corner dial A, a corner dial B and a corner dial C, wherein the corner dial A8 is arranged on a tool lifting lug 7 and used for measuring a corner alpha, the corner dial B9 is arranged on a slide block guiding rotary table 6 and used for measuring a corner beta, and the corner dial C10 is arranged on a combination body consisting of four test piece brackets 5 and used for measuring a corner theta.
The method comprises the following steps:
the tool lifting lug 7 with the rotation angle dial A8 is used for being connected with the two-degree-of-freedom sliding block guiding rotary table 6 through the rotation shaft pin 11 and measuring the rotation angle alpha of the sliding block guiding rotary table 6 around the rotation shaft pin 11, and the rotation angle alpha ranges from 0 to 180 degrees. The slide block guiding rotary table 6 is connected with the tool lifting lug 7 through a rotating shaft pin 11, and can be locked at any angle position by a nut.
The slide guiding turntable 6 can rotate (as shown in fig. 4 (a)), the specific rotation angle beta can be measured through a rotation angle dial B9 on the slide guiding turntable 6, the rotation angle beta ranges from 0 to 360 degrees, and the slide guiding turntable can be manually locked at any angle position by using a clamp.
The two-degree-of-freedom slide block guiding turntable 6 is formed by assembling four guide rail slide blocks 4 and a disc with a slide rail, and the guide rail slide blocks 4 can be locked at any positions of the slide rail. The test piece bracket 5 assembly comprises four test piece brackets 5 with stepped through holes 12 (the through holes can enable the four test piece brackets to be connected end to end by using bolts and nuts), the four test piece brackets 5 are connected end to end by passing through the stepped through holes through the bolts and nuts, the four test piece brackets 5 are fixedly matched with the four guide rail sliding blocks 4 on the sliding block guiding turntable 6 one by one (through bolt thread installation matching), the four frames follow up when the sliding blocks slide, the whole body moves in one degree of freedom, meanwhile, the included angle theta of any two frames can be measured through a dial, the included angle change range is 0-180 degrees, and the position of the test bracket is also fixed after the sliding blocks are locked. The test piece bracket is provided with components and raw materials including but not limited to a single solar cell, a wire, epoxy glue, a coated glass cover plate, a resistor, a silver foil, a polyimide film, a kovar material and the like, and the test pieces are firstly adhered on an aluminum plate and then are arranged on the test piece bracket for fixing.
Example 2
Regarding the locking of the guide rail slide block, the existing slide block locking mechanism can be adopted, namely, the tensioning mechanism with an elastic press block is designed inside the slide block, a screw rod (or a wrench) used for adjusting tensioning is connected with the outside of the slide block, when the slide block needs to slide, the tensioning mechanism is loosened, the slide block can slide, and when the slide block reaches a target position, the slide block can be locked through the screw rod (or the wrench). The specific model of the related guide rail and the guide rail sliding block can be a built-in double-shaft linear motion guide rail model SGR10 and a locking positioning sliding block model SGB10.
The hinge mechanism between the tool lifting lug 7 and the slide block guiding rotary table 6 adopts the existing mechanism, specifically, the slide block guiding rotary table 6 is linked with the tool lifting lug 7 through a threaded rotating shaft pin (or a screw rod), the tool lifting lug 7 is a fixed end, the slide block guiding rotary table 6 can rotate around the shaft (or the screw rod), and the locking mode can be manually locked by adopting a nut.
The hinge mechanism of the slider guide turret 6 is shown in fig. 4 (b). The locking mode adopts a locking clamp which is loose, and a revolute pair of the hinge mechanism is clamped to realize locking.
The working process comprises the following steps:
multi-freedom-degree pose-adjustable electric propulsion plume test tool 1 (shown in figure 2, hereinafter referred to as tool) simulating relative positions of satellite solar cell arrays and electric propellers. Ground tests of damage assessment of the solar array by the electric propeller plume were performed in the vacuum tank 2.
The test piece is fixed on the test piece bracket 5, the angle of the interior angle theta of the test piece bracket 5 can be adjusted by pushing the four guide rail sliders 4 on the slider guide turntable 6, the adjusting range is 0-180 degrees, the angle can be read through the corner dial C8 on the test piece bracket 5, and the guide rail sliders 4 are locked on the guide rail after being adjusted to the target angle. The beta angle posture of the slide block guiding turntable 6 can be rotationally adjusted, the range is 0 to 360 degrees, the angle can be read through the angle dial B9, and the beta angle is locked after being adjusted to the target angle; the alphA-Angle posture of the slide block guiding turntable 6 can be rotationally adjusted around the hinge mechanism, the range is 0 to 180 degrees, the angle can be read through the rotation angle dial A8, and the alphA-Angle is locked after being adjusted to the target angle. And after the posture of the tool 1 is adjusted, all the angles alpha, beta and theta can be known, and all joints are locked.
After the horizontal distance between the tool 1 and the electric propeller 3 is determined, the tool 1 is installed in the vacuum tank body 2 through a tool lifting lug 7 in a welding or riveting mode, vacuumizing is performed, the electric propeller 3 is started to spray plume particles to a test piece on the tool 1 for testing, if the tool 1 is required to be subjected to simple pose adjustment in the test, the guide rail sliding block 4 mechanism can be replaced by a screw rod electric cylinder mechanism, and simple remote angle adjustment is performed outside the tank body.
The technical scheme provided by the embodiment of the application at least has the following technical effects or advantages:
the embodiment can accurately simulate the angle of the satellite electric propeller for carrying out plume injection on any posture of the solar cell array in the ground environment, can be used for adjusting the posture of the electric propeller plume for the solar cell array influence test, and has the characteristics of three-degree-of-freedom adjustment, thereby meeting the current working condition of coupling all satellite electric propulsion plume injection angles with the adjustment diversity of the solar cell array posture, and providing technical support for ground environment simulation for the influence of the electric propeller plume on the solar cell array.
In summary, the application provides an electric propulsion plume test tool with multiple degrees of freedom and adjustable pose.
The foregoing examples illustrate the application in detail, but are merely preferred embodiments of the application and are not to be construed as limiting the scope of the application. All equivalent changes and modifications within the scope of the present application are intended to be covered by the present application.
Claims (5)
1. An electric propulsion plume test tool with multiple degrees of freedom and adjustable pose is characterized in that: the utility model provides a multi freedom position appearance adjustable electricity impels plume test fixture includes the frock, the frock includes test piece bracket, slider direction revolving stage and frock lug, slider direction revolving stage one side is equipped with the track of "cross" font, and the another side is equipped with hinge mechanism, slider direction revolving stage can follow hinge mechanism's center pin rotation, hinge mechanism passes through the pivot pin with the frock lug to be connected, test piece bracket is rectangular frame structure, the quantity of test piece bracket is four and the frame that the cross section is diamond is constituteed to the head and the tail each other in the articulated, the four corners department of frame is equipped with the guide rail slider, the guide rail slider can follow the track and remove.
2. The multi-degree-of-freedom pose-adjustable electric propulsion plume test tool according to claim 1, wherein the tool is characterized in that: the tool is arranged in a vacuum tank body, and an electric propeller in the vacuum tank body can spray plume particles to the tool.
3. The multi-degree-of-freedom pose-adjustable electric propulsion plume test tool according to claim 1, wherein the tool is characterized in that: be equipped with corner calibrated scale A on the frock lug, corner calibrated scale A's zero scale mark is parallel with the axis of frock lug.
4. The multi-degree-of-freedom pose-adjustable electric propulsion plume test tool according to claim 1, wherein the tool is characterized in that: and a corner dial B is arranged on the slide block guiding turntable.
5. The multi-degree-of-freedom pose-adjustable electric propulsion plume test tool according to claim 1, wherein the tool is characterized in that: the frame is provided with a corner dial C at one corner, and zero scale lines of the corner dial C are parallel to one side of the frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111587813.1A CN114264446B (en) | 2021-12-23 | 2021-12-23 | Multi-degree-of-freedom pose-adjustable electric propulsion plume test tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111587813.1A CN114264446B (en) | 2021-12-23 | 2021-12-23 | Multi-degree-of-freedom pose-adjustable electric propulsion plume test tool |
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| Publication Number | Publication Date |
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| CN114264446A CN114264446A (en) | 2022-04-01 |
| CN114264446B true CN114264446B (en) | 2023-08-29 |
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| CN202111587813.1A Active CN114264446B (en) | 2021-12-23 | 2021-12-23 | Multi-degree-of-freedom pose-adjustable electric propulsion plume test tool |
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|---|---|---|---|---|
| GB2056392A (en) * | 1979-08-22 | 1981-03-18 | Rca Corp | Attitude control system for spacecraft utilizing the thruster plume |
| EP1059231A2 (en) * | 1999-06-08 | 2000-12-13 | Space Systems / Loral, Inc. | Solar array control for a satellite with an electric propulsion system |
| CN101876615A (en) * | 2009-12-17 | 2010-11-03 | 中国航天科技集团公司第五研究院第五一○研究所 | Method for monitoring plume contamination of attitude control engine of spacecraft |
| CN101936806A (en) * | 2010-07-21 | 2011-01-05 | 北京航空航天大学 | Measurement device for aerodynamic force of attitude control motor plume on large-sized solar cell wing |
| CN205785823U (en) * | 2016-05-18 | 2016-12-07 | 北京航天试验技术研究所 | A kind of space propulsion plume measures heat flow transducer fixing device |
| CN108387260A (en) * | 2017-12-20 | 2018-08-10 | 中国空间技术研究院 | A kind of electric propulsion plume testing appraisal procedure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7059571B2 (en) * | 2003-02-21 | 2006-06-13 | The Boeing Company | Deployable spacecraft mount for electric propulsion |
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2021
- 2021-12-23 CN CN202111587813.1A patent/CN114264446B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2056392A (en) * | 1979-08-22 | 1981-03-18 | Rca Corp | Attitude control system for spacecraft utilizing the thruster plume |
| EP1059231A2 (en) * | 1999-06-08 | 2000-12-13 | Space Systems / Loral, Inc. | Solar array control for a satellite with an electric propulsion system |
| CN101876615A (en) * | 2009-12-17 | 2010-11-03 | 中国航天科技集团公司第五研究院第五一○研究所 | Method for monitoring plume contamination of attitude control engine of spacecraft |
| CN101936806A (en) * | 2010-07-21 | 2011-01-05 | 北京航空航天大学 | Measurement device for aerodynamic force of attitude control motor plume on large-sized solar cell wing |
| CN205785823U (en) * | 2016-05-18 | 2016-12-07 | 北京航天试验技术研究所 | A kind of space propulsion plume measures heat flow transducer fixing device |
| CN108387260A (en) * | 2017-12-20 | 2018-08-10 | 中国空间技术研究院 | A kind of electric propulsion plume testing appraisal procedure |
Non-Patent Citations (1)
| Title |
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Effective date of registration: 20221116 Address after: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Applicant after: CETC Energy Co.,Ltd. Address before: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Applicant before: The 18th Research Institute of China Electronics Technology Group Corporation Applicant before: CETC Energy Co.,Ltd. |
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Address after: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Applicant after: CETC Blue Sky Technology Co.,Ltd. Address before: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Applicant before: CETC Energy Co.,Ltd. |
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